System for protecting turbine engine surfaces from corrosion

1. A system, comprising:

a turbine engine component comprising a first material having a surface exposed to a fluid flow path, wherein the fluid flow path is disposed within a turbine engine; and

a sacrificial anode layer disposed on the surface, wherein the sacrificial anode layer comprises a second material that is electrochemically more active than the first material, and the second material is configured to preferentially corrode to protect the first material from corrosion.

2. The system of claim 1 , wherein the sacrificial anode layer comprises a patterned layer of the second material.

3. The system of claim 2 , wherein the patterned layer comprises a plurality of sacrificial anode portions that are connected to one another.

4. The system of claim 2 , wherein the patterned layer comprises a plurality of sacrificial anode portions that are disconnected from one another.

5. The system of claim 2 , wherein the patterned layer comprises a patterned coating continuously adhered to the surface.

6. The system of claim 1 , wherein the sacrificial anode layer comprises a third material that is electrochemically more active than the first material and the second material.

7. The system of claim 6 , wherein the second material is disposed in a first pattern of a plurality of first sacrificial anode portions, the third material is disposed in a second pattern of a plurality of second sacrificial anode portions, and the first and second sacrificial anode portions are disposed side by side or one over another relative to the surface.

8. The system of claim 1 , wherein the second material is at least greater than approximately 10 percent more electrochemically active than the first material.

9. The system of claim 1 , wherein the second material comprises carbon steel, aluminum, mixed metal oxides, or a combination thereof.

10. The system of claim 1 , wherein the turbine engine component is a part of a gas turbine combustor or a gas turbine section of a gas turbine engine, and the fluid flow path is a combustion gas path.

11. A system, comprising:

a gas turbine engine comprising a first material having a surface exposed to a flow path of hot condensing combustion gas; and

a patterned anode layer comprising a second material disposed on the surface, wherein the patterned anode layer is configured to protect the surface from corrosion by the hot condensing combustion gas.

12. The system of claim 11 , wherein the second material is electrochemically more active than the first material, and the second material is configured to preferentially corrode to protect the first material from corrosion by the hot condensing combustion gas.

13. The system of claim 11 , comprising a power source that supplies power to a transformer rectifier coupled to the patterned anode layer, wherein the transformer rectifier is configured to impress a current through the patterned anode layer to actively protect the first material from corrosion by the hot condensing combustion gas.

14. The system of claim 11 , wherein the patterned anode layer is recessed into the surface to provide a smooth surface along the flow path.

15. The system of claim 11 , wherein the patterned anode layer comprises a grid of the second material.

16. The system of claim 15 , wherein the grid is a printed grid continuously adhered to the surface.

17. The system of claim 11 , wherein the patterned anode layer comprises a third material that is different than the first and second materials.

18. A system, comprising:

a patterned anode layer configured to protect a surface of a as turbine engine from corrosion by hot condensing combustion gas;

a reference electrode in contact with the hot condensing combustion gas; and

a controller configured to adjust a current to the patterned anode layer in response to feedback from the reference electrode.

19. The system of claim 18 , comprising the gas turbine engine having the surface.

20. The system of claim 18 , wherein the feedback from the reference electrode is indicative of an electrical potential difference across the reference electrode and the as turbine engine.